Rigidity Evaluation Model for Aircraft Structural Parts Web Based on Beam Bending Theory

DOI

10.2991/icmse-18.2018.102How to use a DOI?

Keywords

Aircraft structural part; model of beam bending; closed web; open web; rigidity

Abstract

Based on theories of beam bending, a quantitative evaluation method for web rigidity based on aircraft structural part geometrical features and process features was proposed. Combined with the characteristics of cutting force of web features in aircraft structural parts and the basic theory of simply supported beam and cantilever beam, a rigidity evaluation model for closed and open pocket bottom was set up; and a rigidity calculation model for bottom of rectangle and circle pocket was established. The machining deformation of open and closed rectangular webs was analyzed using the ABAQUS software, and the accuracy of rigidity calculation model was Validated by the simulation results. The web rigidity evaluation model can provide theoretical reference for aircraft structural part web rigidity judgment, clamping scheme and cutting parameters optimization.

Copyright

© 2018, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Qinghong Gong
AU  - Chao Sun
AU  - Wenping Mou
PY  - 2018/05
DA  - 2018/05
TI  - Rigidity Evaluation Model for Aircraft Structural Parts Web Based on Beam Bending Theory
BT  - Proceedings of the 2018 8th International Conference on Manufacturing Science and Engineering (ICMSE 2018)
PB  - Atlantis Press
SP  - 551
EP  - 558
SN  - 2352-5401
UR  - https://doi.org/10.2991/icmse-18.2018.102
DO  - 10.2991/icmse-18.2018.102
ID  - Gong2018/05
ER  -